Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor

Junhai, Li; Yu, Nanjia; Zeng, Peng; Cai, Guobiao

doi:10.1007/s11431-013-5156-y

Cited by 16 publications

(3 citation statements)

References 17 publications

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“…Karimi et al [8,9] investigated a pressurized system with a special capsule stored by high-pressure gas in the upper-stage engine and proved that the heat exchanger installed in front of the tank can improve the performance of the pressurized system. Li et al [10] considered a pressurized feed system of the dual-thrust hybrid rocket motor and studied the influences of some structural and initial state parameters on the performance of the motor.…”

Section: Introductionmentioning

confidence: 99%

Characteristics of a Heat Exchanger in a Liquid Rocket Engine Using Conjugate Heat Transfer Coupling with Open-Source Tools

Jeong,

Jang,

Kim

2023

Aerospace

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Since a heat exchanger used in a gas generator of an open-cycle liquid rocket engine was operated in a high-temperature environment, the coupled analysis for heat transfer characteristics and structural integrity should be performed simultaneously. For these reasons, a numerical analysis of the heat exchanger in a liquid rocket engine was performed to elucidate the effects of heat transfer and structural deformation simultaneously using conjugate heat transfer (CHT) analysis and open-source tools. For the baseline heat exchanger, which had an inner helically coiled tube with nine turns (Nc=9), the heat transfer characteristics were investigated and findings showed that the heat transfer performance was reduced from the sixth turn. Further analysis was performed to examine the effect of the number of turns in terms of heat flux and the corresponding pressure drop and the weight of the structure. The results indicated that the heat exchanger with Nc=3 had a significantly reduced outlet temperature due to an excessively shortened flow residence time. The heat exchanger with Nc=6 showed an outlet temperature similar to that of the baseline; it also presented advantages in terms of the pressure drop and structure weight. In addition, the thermal deformation and stress caused by temperature changes were numerically investigated to consider the structural integrity of the heat exchanger with Nc=3,6,9. Further numerical analyses were performed at various flow rates. As the flow rate of helium increased, the amount of heat received from the high-temperature exhaust gas from the gas generator increased but the outlet temperature of helium decreased gradually. Finally, the temperature difference between the outer and inner walls increased due to the high heat flux in the region around the inlet, resulting in an increase in thermal stress. Based on these results, the optimal shape and flow rate of the system were identified. Furthermore, the heat transfer performance was found to correlate with the flow characteristics of the coiled tube.

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Section: Introductionmentioning

confidence: 99%

Characteristics of a Heat Exchanger in a Liquid Rocket Engine Using Conjugate Heat Transfer Coupling with Open-Source Tools

Jeong,

Jang,

Kim

2023

Aerospace

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“…Many intensive studies have been conducted on key technologies for HRM [4][5][6][7][8] and its applications [9][10][11]. In an interesting demonstration test that was recently conducted in the United States, the ascent, hovering, and soft landing of a craft were accomplished using an HRM as the propulsion system.…”

Section: Introductionmentioning

confidence: 99%

Uncertainty analysis and probabilistic design optimization of hybrid rocket motors for manned lunar landing

Zhu

Tian

Cai

et al. 2015

Sci. China Technol. Sci.

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To obtain a conceptual design for a hybrid rocket motor (HRM) to be used as the Ascent Propulsion System in the Apollo lunar module, the deterministic design optimization (DDO) method is applied to the HRM design. Based on the results of an uncertainty analysis of HRMs, an uncertainty-based design optimization (UDO) method is also adopted to improve the design reliability. The HRM design process, which is a multidisciplinary system, is analyzed, and a mathematical model for the system design is established to compute the motor performance from the input parameters, including the input variables and model parameters. The input parameter uncertainties are quantified, and a sensitivity analysis of the model parameter uncertainties is conducted to identify the most important model parameter uncertainties for HRMs. The DDO and probabilistic UDO methods are applied to conceptual designs for an HRM to be used as a substitute for the liquid rocket motor (LRM) of the Ascent Propulsion System. The conceptual design results show that HRMs have several advantages as an alternative to the LRM of the Ascent Propulsion System, including nontoxic propellant combination, small motor volume, and comparable functions, such as restarting and throating. Comparisons of the DDO and UDO results indicate that the UDO method achieves more robust and reliable optimal designs than the DDO method. The probabilistic UDO method can be used to develop better conceptual designs for HRMs. hybrid rocket motor, deterministic design optimization, uncertainty-based design optimization, sensitivity analysis, manned lunar landing Citation: Zhu H, Tian H, Cai G B, et al. Uncertainty analysis and probabilistic design optimization of hybrid rocket motors for manned lunar landing. Sci

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“…YBRID rocket motor has become an attractive choice for numerous applications for its safety, low coast, low toxicity and restart characteristics [1][2][3][4][5][6] . It has great prospect in the application fields of sounding rockets, target drones, commercial manned spaceships, and so on.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional Numerical Simulation of Two-phase Flow in Hybrid Rocket Motor

Tian

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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This paper presents the three-dimensional numerical simulation of hybrid rocket motor with hydrogen peroxide (H 2 O 2 ) as the liquid oxidizer and hydroxyl terminated polybutadiene (HTPB) as the solid fuel. Two kinds of injector patterns are designed for the motor. The injector holes of pattern A are distributed along the projection of the fuel surface to the injector panel, and injector pattern B refers to the almost equal spaced holes design. The star fuel grain is selected for the simulation and half a star is chosen as the computational domain. The Euler-Lagrange approach is used for the two-phase flow. The droplet evaporation and decomposition, solid fuel pyrolysis, gaseous chemical reactions, and turbulence are considered in the simulation model. A series of simulation cases are performed for the two kinds of injector patterns with different droplet diameter and injection velocity. The results of the temperature contours, species mass fractions, droplet traces, fuel regression rate distributions, and combustion efficiencies are presented. For the injector pattern A, most of the droplets are injected into the fuel port and they are distributed near the fuel surface in the fuel port. On the contrary, some droplets spray directly onto the forward fuel end for the injector pattern B, and in the fuel port, the oxidizer mainly concentrates in the central area. This implies that the oxidizer and fuel of the motor with injector pattern A can be mixed better. With the increasing of the droplet diameter, the droplet residence time and distance in the combustion chamber will both increase. The increasing of the injection velocity does not affect the residence distance obviously, yet it reduces the droplet residence time with rapid velocity. In the variation range simulated, the increasing of the droplet diameter and injection velocity will both decrease the mixing of the reactants and reduce the combustion efficiency, which is more obvious for the injector pattern B. In addition, the combustion efficiency of the motor with injector pattern A is higher than that with injector pattern B, which indicates that injector pattern A may be an effective scheme in the hybrid rocket motor design. Nomenclature A = Arrhenius pre-exponential constant C = concentration E = activation energy F = force e = energy H = source term k = kinetic energy of turbulent fluctuations M = molecular weight p = pressure , i r R = rate of production of species i due to reaction r r = fuel regression rate T = temperature 1 Ph.D. Student, 2 t = time u = velocity X = mole fraction , , x y z = coordinate system Y = mass fraction ε = turbulence dissipation rate ρ = density , i r ν ′ = stoichiometric coefficient for reactant i in reaction r , i r ν ′′ = stoichiometric coefficient for product i in reaction r µ = viscosity λ = thermal conductivity η = efficiency Subscripts d = droplet f = fuel g = gas products , , i j k = index o = oxidizer P = product R = reactant r = reaction s = fuel surface sat = saturated

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Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor

Cited by 16 publications

References 17 publications

Characteristics of a Heat Exchanger in a Liquid Rocket Engine Using Conjugate Heat Transfer Coupling with Open-Source Tools

Characteristics of a Heat Exchanger in a Liquid Rocket Engine Using Conjugate Heat Transfer Coupling with Open-Source Tools

Uncertainty analysis and probabilistic design optimization of hybrid rocket motors for manned lunar landing

Three-dimensional Numerical Simulation of Two-phase Flow in Hybrid Rocket Motor

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